DEN89FA152
1989-07-02 · ANGEL FIRE, New Mexico, United States · Fatal · 1 aircraft · Status: Completed
Airport AXX
N20CF has since been reassigned. It is now registered to a different aircraft (CESSNA 170B), which was not involved in this event.
Aircraft involved
Probable cause & findings
IMPROPER PLANNING/DECISION BY THE PILOT, HIS PREMATURE ROTATION FOR TAKEOFF AND SUBSEQUENT FAILURE TO OBTAIN OR MAINTAIN SUFFICIENT SPEED TO CLIMB, AND HIS FAILURE TO ABORT THE TAKEOFF (WHILE THERE WAS SUFFICIENT RWY REMAINING). CONTRIBUTING FACTORS WERE: THE PILOT ALLOWED THE AIRCRAFT GROSS WEIGHT TO EXCEED THE MAXIMUM LIMIT, HIGH DENSITY ALTITUDE, UPHILL RUNWAY GRADIENT, DOWNDRAFT, TURBULENCE, AND TREES.
Factual narrative
THE PLT AND 3 PAX BOARDED THE ACFT AT ANGEL FIRE, NM (ELEV 8382 FT MSL) TO RETURN TO PHOENIX, AZ. DENSITY ALT WAS APRX 11,582 FT MSL. THE ACFT, WHICH HAD JUST BEEN SERVICED, HAD 54 GAL OF FUEL ON BOARD AND WAS APRX 30 LBS OVER ITS MAX GROSS WEIGHT LIMIT. THE PLT ELECTED TO TAKE OFF ON RWY 17 (8900 FT X 75 FT, 0.643% UPHILL GRADIENT). HE ROTATED 3 TIMES BEFORE THE ACFT FINALLY LIFTED OFF NEAR THE DEPARTURE END. NUMEROUS WITNESSES OBSERVED THE ACFT FLYING LOW THROUGH THE VALLEY TOWARDS GRADUALLY RISING TERRAIN. IT FINALLY STRUCK TREES AND CRASHED APRX 5 MI FROM THE ARPT AT AN ELEV OF 8813 FT MSL. ONE PAX WAS FATALLY INJURED WHILE ATTEMPTING TO EVACUATE THE BURNING ACFT. PERFORMANCE CHARTS INDICATED THE ACFT WAS CAPABLE OF TAKING OFF UNDER THE PREVAILING CONDITIONS. THE PLT LATER REPORTED THAT TURBULENCE AND DOWNDRAFTS DEGRADED THE ACFT'S CLIMB PERFORMANCE. HE ALSO INDICATED THE ACFT WAS ON THE VERGE OF STALLING THROUGHOUT THE SHORT FLT. Source: NTSB Aviation Accident Database (Pre-2008 Archive) Retrieved: 2026-02-12
Verbatim from NTSB's published report. Source file
NTSB_1989_DEN89FA152.txt.
Findings + structured fields enriched from FAA avall.mdb.
Full investigation docket on
data.ntsb.gov ↗.
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Related research
Matched on aircraft type or causal vocabulary (stall, turbulence). All research papers
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Aerodynamic prediction of glaze ice accretion on airfoils and wing is studied using the Reynolds-averaged Navier-Stokes method.
- NASA NTRS 2019 · Conference Paper Prediction of stall and post-stall behavior of airfoils at low and high Reynolds numbers
An interactive boundary-layer method, together with the e(super n)-approach to the calculation of transition, has been used to predict the stall and post-stall behavior of airfoils at low and high Rey…
- arXiv 2026 · arXiv preprint Direct Numerical Simulations of Ice-Ocean Boundary Turbulence
Turbulent heat and freshwater transport at ice-ocean interfaces controls glacier and iceberg melt rates, yet the underlying physics remains poorly constrained.
- NASA NTRS 2026 · Conference Paper Computational Analysis of Steady State Aerodynamics of Transonic Truss-Braced Wing Configuration in Deep Stall
This study presents a computational investigation of steady state aerodynamics of the Subsonic Ultra-Green Aircraft Research (SUGAR) Transonic Truss-Braced Wing (TTBW) configuration over a wide range …
- arXiv 2025 · arXiv preprint Explainable LiDAR 3D Point Cloud Segmentation and Clustering for Detecting Airplane-Generated Wind Turbulence
Wake vortices - strong, coherent air turbulences created by aircraft - pose a significant risk to aviation safety and therefore require accurate and reliable detection methods.